WO2020259010A1 - Framework apparatus and fiber-optic gyroscope inertia device having same - Google Patents
Framework apparatus and fiber-optic gyroscope inertia device having same Download PDFInfo
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- WO2020259010A1 WO2020259010A1 PCT/CN2020/084845 CN2020084845W WO2020259010A1 WO 2020259010 A1 WO2020259010 A1 WO 2020259010A1 CN 2020084845 W CN2020084845 W CN 2020084845W WO 2020259010 A1 WO2020259010 A1 WO 2020259010A1
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- optic gyroscope
- fiber optic
- support
- heat dissipation
- hollow frame
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/58—Turn-sensitive devices without moving masses
- G01C19/64—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams
- G01C19/72—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams with counter-rotating light beams in a passive ring, e.g. fibre laser gyrometers
- G01C19/721—Details
- G01C19/722—Details of the mechanical construction
Definitions
- the invention relates to an inertial measurement device, in particular to a skeleton device and an optical fiber gyroscope inertial device with the skeleton device.
- Fiber optic gyroscope is an angular rate measuring instrument based on the Sagnac effect. It has the technical advantages of simple structure, impact resistance, and large dynamic range. At the same time, it has low cost, long life and high reliability. It has been widely used in Aerospace, robot control, oil and coal mining and other fields.
- temperature of the fiber optic gyroscope changes, it will affect the measurement accuracy of the fiber optic gyroscope. For this reason, domestic and foreign researchers have done a lot of research on temperature drift error compensation of fiber optic gyroscopes.
- the spatial layout and heat dissipation performance of the inertial device skeleton also have an important impact on the stability of the fiber optic gyroscope. Therefore, it is urgent to design an effective and easy-to-engineer fiber optic gyroscope skeleton device to improve the environmental adaptability of the fiber optic gyroscope.
- the present invention provides a skeleton device with reasonable spatial layout, sufficient heat dissipation space, and capable of effectively improving the environmental adaptability of the fiber optic gyroscope.
- Another object of the present invention is to provide an optical fiber gyroscope inertial device with the above-mentioned skeleton device.
- the skeleton device of the present invention includes a skeleton body and a ring-type fixed support; the skeleton body has a base and a hollow frame extending upward from the upper surface of the base; the hollow frame is hollow and has an open top
- the hollow frame has a support assembly plane; the ring-type fixed support is installed on the support assembly plane, and the hollow inner cavity of the hollow frame is divided into two upper and lower chambers, the two chambers They are respectively a fiber optic gyroscope containing cavity located at the lower part and a power supply assembly containing cavity located at the upper part; each side wall of the hollow frame has an upper heat dissipation hole and a lower heat dissipation hole, and the upper heat dissipation hole penetrates to the power supply assembly container.
- a cavity, the lower heat dissipation hole penetrates to the accommodating cavity of the fiber optic gyroscope.
- each side wall of the hollow frame is provided with a concave platform, and the inner surface of the two adjacent side walls is connected with an assembly platform, and the concave platform and the assembly platform are located on the same horizontal plane.
- the recessed platform and the assembly platform jointly form the assembly plane of the support.
- the ring-type fixed support has a support main body and a heat dissipation connection hole, the support main body is arranged on the assembly platform, and the heat dissipation connection hole penetrates and is arranged in the middle position of the support main body.
- the ring-type fixed support member further has positioning side wings corresponding to the recessed platform one-to-one, and the positioning side wings extend from the main body of the support member to the corresponding recessed platform and are clamped in the recessed platform.
- the ring-type fixed support member also has a plurality of bolt holes for installing and fixing the power supply assembly, and the bolt holes are scattered on the surface of the ring-type fixed support member.
- connection stud for fixing the fiber optic gyroscope is provided at the connection of the inner surfaces of the two adjacent side walls of the hollow frame, and the connection stud is located below the assembly platform.
- the inner surface of the side wall of the hollow frame located below the mounting plane of the support has an arc-shaped part, which defines the inner diameter of the accommodating cavity of the fiber optic gyroscope.
- the hollow frame is a rectangular parallelepiped hollow frame.
- the technical solution adopted by the fiber optic gyroscope inertial device with the skeleton device according to the present invention includes a fiber optic gyroscope, a power module, a circuit board and a cover, and the fiber optic gyroscope is fixed upside down on the The fiber optic gyroscope accommodating cavity; the power module and the circuit board are both arranged in the power component accommodating cavity and fixed on the ring-type fixed support; after the fiber optic gyroscope line passes through the heat dissipation wiring hole It is connected to the circuit board; the cover is arranged on the outside of the hollow frame from top to bottom, and is hermetically connected with the base.
- the outer diameter of the fiber optic gyroscope is consistent with the inner diameter of the accommodating cavity of the fiber optic gyroscope.
- the frame device is provided with a ring-type fixed support and a hollow frame with a hollow and open upper end, and the hollow inner cavity of the hollow frame is divided into an optical fiber gyroscope accommodating cavity and a power supply component accommodating cavity by the ring-type fixed support.
- Fiber optic gyroscopes and power supply components provide reasonable assembly space to avoid waste of space layout.
- heat dissipation holes are hollowed out on each side wall of the hollow frame to provide enough heat dissipation space.
- the heat emitted by the fiber optic gyroscope and power supply assembly can flow freely at the openings on the side walls and the top to avoid excessive local heat.
- the measurement accuracy has an impact, so that the fiber optic gyroscope inertial device equipped with the skeleton device has higher reliability and environmental adaptability.
- Figure 1 is a schematic diagram of the skeleton body structure of the present invention.
- Figure 2 is a schematic top view of the skeleton body structure of the present invention.
- Figure 3 is a schematic view of the structure of the ring-type fixed support of the present invention.
- FIG. 4 is a schematic diagram of the internal structure of the fiber optic gyroscope inertial device of the present invention.
- FIG. 5 is a schematic diagram of the structure of the fiber optic gyroscope in the present invention.
- FIG. 6 is a schematic diagram of the overall structure of the fiber optic gyroscope inertial device of the present invention.
- Fig. 7 is an exploded view of the internal structure of the fiber optic gyroscope inertial device of the present invention.
- this embodiment discloses an optical fiber gyroscope inertial device, which has a skeleton device, an optical fiber gyroscope 10, a power module 11, a circuit board 12, and a cover 13.
- the skeleton device includes a skeleton body 1 and a ring-type fixed support 2.
- the skeleton body 1 has a base 3 and a hollow frame 4, and the hollow frame 4 extends upward from the upper surface of the base 3.
- the hollow frame 4 has a hollow rectangular parallelepiped structure with an open top.
- a recess 43 is provided in the middle of the inner surface of the four side walls, and an assembly platform 44 is provided at the junction of the inner surfaces of two adjacent side walls.
- the recess 43 and the assembly platform 44 are located on the same horizontal plane, and the horizontal plane defines the position of the support assembly plane inside the hollow frame 4.
- the side wall of the hollow frame 4 is provided with an upper heat dissipation hole 41 and a lower heat dissipation hole 42.
- the ring-type fixed support 2 is installed in the assembly plane of the support, and separates the hollow cavity of the hollow frame 4 into a fiber optic gyroscope accommodating cavity at the lower part and a power supply component accommodating cavity at the upper part.
- the upper heat dissipation hole 41 communicates with the power supply assembly accommodating cavity
- the lower heat dissipation hole 42 communicates with the fiber optic gyroscope accommodating cavity.
- the ring-type fixed support 2 has a support main body 21, a heat dissipation wiring hole 22, a positioning side wing 23 and a plurality of bolt holes 24.
- the four corners of the support body 21 are respectively arranged on the four assembly platforms 44, and the four positioning side wings 23 are respectively clamped in the four recessed platforms 43, so that the ring-type fixed support 2 is fixed.
- the heat dissipation wiring hole 22 is opened in the middle position of the support body 21, on the one hand, it is used for wiring wiring, and on the other hand, it provides an upward flow path for the heat in the accommodating cavity of the lower fiber optic gyroscope.
- the bolt holes 24 are scattered on the upper surface of the ring-type fixing support 2, and are used to fix the power module 11 and the circuit board 12, and the bolt holes 24 for fixing the power module 11 and the circuit board 12 are arranged in a staggered manner. There is enough distance to not interfere with each other.
- the fiber optic gyroscope 10 has a roughly cylindrical structure, and its side wall is provided with a screw hole 101 that is matched with a connecting stud 45, and the connecting stud 45 is arranged at the connection of the inner surface of the side wall below the assembly platform 44 ,
- the fiber optic gyroscope 10 can be fixed by connecting the two with screws.
- the fiber optic gyroscope 10 is installed upside down in the fiber optic gyroscope housing cavity, and the arc-shaped part of the inner surface of the side wall of the hollow frame 4 abuts against the outer circumference of the fiber optic gyroscope 10.
- the diameter of is consistent with the outer diameter of the fiber optic gyroscope 10, so as to avoid excessive space and size waste due to excessive gaps between the two during manufacturing or assembly.
- the power supply assembly composed of the power supply module 11 and the circuit board 12 is arranged in the power supply assembly accommodating cavity, and is connected and fixed to different bolt holes 24 of the ring-type fixing support 2 by screws 15 respectively.
- the line of the fiber optic gyroscope 10 passes through the heat dissipation wiring hole 22 and then is connected to the circuit board 12, and the power module 11 provides power.
- the circuit board 12 is fixed to the fiber optic gyroscope 10 through the ring-type fixed support 2 to achieve resonance, which can reduce additional factors that affect the measurement accuracy of the fiber optic gyroscope 10.
- the cover 13 is arranged on the outside of the hollow frame 4 from top to bottom, and is sealed with the base 3 by a sealing ring, and the fixing ears of the two are connected by screws to complete the assembly and fixing.
- the general cover 13 is used to prevent moisture and improve the impact resistance of the fiber optic gyroscope inertial device, and its thin thickness will not affect heat dissipation.
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- Optics & Photonics (AREA)
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Abstract
A framework apparatus and a fiber-optic gyroscope inertia device having same. The framework apparatus is provided with an annular fixed supporting member (2) and a hollow framework (4) which is hollowed out and has an open upper end; a hollow inner cavity of the hollow framework (4) is separated into a fiber-optic gyroscope accommodating cavity and a power supply assembly accommodating cavity by means of the annular fixed supporting member (2), so as to provide reasonable assembly spaces for a fiber-optic gyroscope and a power supply assembly, and avoid waste of spatial layout; heat dissipation holes (41, 42) are formed in side walls of the hollow framework (4) in a hollowed manner, so that a sufficient heat dissipation space is provided, heat emitted from the fiber-optic gyroscope (10) and the power supply assembly can flow freely via the holes in the side walls and the top part, and the measurement precision is prevented from being affected because the local heat is too high. Therefore, the fiber-optic gyroscope inertia device equipped with the framework apparatus has the advantages of high reliability and environmental adaptability.
Description
本发明涉及一种惯性测量装置，具体涉及一种骨架装置以及具有该骨架装置的光纤陀螺惯性器件。The invention relates to an inertial measurement device, in particular to a skeleton device and an optical fiber gyroscope inertial device with the skeleton device.
光纤陀螺仪是基于Sagnac效应的角速率测量仪表，其具有结构简单、耐冲击、动态范围大的技术优点，同时具有成本低、寿命长、可靠性高的使用效果，现已被广泛的应用在航空航天、机器人控制、石油煤炭开采等多个领域。当光纤陀螺仪工作环境温度发生变化时，会对光纤陀螺仪的测量精度产生影响。为此国内外研究人员，对光纤陀螺仪温度漂移误差补偿方面做了大量研究。然而惯性器件骨架的空间布局和散热性能亦对光纤陀螺仪的稳定性产生重要影响。为此，迫切需要设计一种有效且易于工程实现的光纤陀螺仪骨架装置以提升光纤陀螺的环境适应性。Fiber optic gyroscope is an angular rate measuring instrument based on the Sagnac effect. It has the technical advantages of simple structure, impact resistance, and large dynamic range. At the same time, it has low cost, long life and high reliability. It has been widely used in Aerospace, robot control, oil and coal mining and other fields. When the working environment temperature of the fiber optic gyroscope changes, it will affect the measurement accuracy of the fiber optic gyroscope. For this reason, domestic and foreign researchers have done a lot of research on temperature drift error compensation of fiber optic gyroscopes. However, the spatial layout and heat dissipation performance of the inertial device skeleton also have an important impact on the stability of the fiber optic gyroscope. Therefore, it is urgent to design an effective and easy-to-engineer fiber optic gyroscope skeleton device to improve the environmental adaptability of the fiber optic gyroscope.
发明内容Summary of the invention
发明目的：为了克服现有技术的缺陷，本发明提供一种骨架装置，该骨架装置空间布局合理，具有充足的散热空间，能够有效提升光纤陀螺仪的环境适应性。Objective of the invention: In order to overcome the defects of the prior art, the present invention provides a skeleton device with reasonable spatial layout, sufficient heat dissipation space, and capable of effectively improving the environmental adaptability of the fiber optic gyroscope.
本发明的另一目的是提供一种具有上述骨架装置的光纤陀螺惯性器件。Another object of the present invention is to provide an optical fiber gyroscope inertial device with the above-mentioned skeleton device.
技术方案：本发明所述的一种骨架装置，包括骨架本体和环式固定支撑件；所述骨架本体具有底座、自底座上表面向上延伸出的镂空框架；所述镂空框架呈中空且顶端开口的结构，镂空框架内具有支撑件装配平面；所述环式固定支撑件安装于该支撑件装配平面上，并将镂空框架的中空内腔分隔出上下两个腔室，所述两个腔室分别为位于下部的光纤陀螺仪容置腔以及位于上部的电源组件容置腔；所述镂空框架的各个侧壁均具有上部散热孔和下部散热孔，所述上部散热孔贯通至所述电源组件容置腔，所述下部散热孔贯通至所述光纤陀螺仪容置腔。Technical Solution: The skeleton device of the present invention includes a skeleton body and a ring-type fixed support; the skeleton body has a base and a hollow frame extending upward from the upper surface of the base; the hollow frame is hollow and has an open top The hollow frame has a support assembly plane; the ring-type fixed support is installed on the support assembly plane, and the hollow inner cavity of the hollow frame is divided into two upper and lower chambers, the two chambers They are respectively a fiber optic gyroscope containing cavity located at the lower part and a power supply assembly containing cavity located at the upper part; each side wall of the hollow frame has an upper heat dissipation hole and a lower heat dissipation hole, and the upper heat dissipation hole penetrates to the power supply assembly container. A cavity, the lower heat dissipation hole penetrates to the accommodating cavity of the fiber optic gyroscope.
其中，所述镂空框架的各个侧壁的内表面均设置有凹台，相邻的两个所述侧壁的内表面连接处均具有装配平台，所述凹台和所述装配平台位于同一水平面，凹台和装配平台共同形成所述支撑件装配平面。Wherein, the inner surface of each side wall of the hollow frame is provided with a concave platform, and the inner surface of the two adjacent side walls is connected with an assembly platform, and the concave platform and the assembly platform are located on the same horizontal plane. , The recessed platform and the assembly platform jointly form the assembly plane of the support.
所述环式固定支撑件具有支撑件主体和散热接线孔，所述支撑件主体设置在所述装配平台上，所述散热接线孔贯穿的设置于支撑件主体的中间位置。The ring-type fixed support has a support main body and a heat dissipation connection hole, the support main body is arranged on the assembly platform, and the heat dissipation connection hole penetrates and is arranged in the middle position of the support main body.
所述环式固定支撑件还具有与所述凹台一一对应的定位侧翼，所述定位侧翼自所述支撑件主体向对应的凹台延伸，并卡设在凹台内。The ring-type fixed support member further has positioning side wings corresponding to the recessed platform one-to-one, and the positioning side wings extend from the main body of the support member to the corresponding recessed platform and are clamped in the recessed platform.
所述环式固定支撑件还具有多个用于安装固定电源组件的螺栓孔，所述螺栓孔分散布置于该环式固定支撑件的表面。The ring-type fixed support member also has a plurality of bolt holes for installing and fixing the power supply assembly, and the bolt holes are scattered on the surface of the ring-type fixed support member.
所述镂空框架的相邻的两个侧壁的内表面连接处设置有用于固定光纤陀螺仪的连接螺柱，所述连接螺柱位于所述装配平台下方。A connection stud for fixing the fiber optic gyroscope is provided at the connection of the inner surfaces of the two adjacent side walls of the hollow frame, and the connection stud is located below the assembly platform.
所述镂空框架位于所述支撑件装配平面下方的侧壁内表面具有呈圆弧形的部分，该部分限定了所述光纤陀螺仪容置腔的内径。The inner surface of the side wall of the hollow frame located below the mounting plane of the support has an arc-shaped part, which defines the inner diameter of the accommodating cavity of the fiber optic gyroscope.
进一步的，所述镂空框架为长方体形镂空框架。Further, the hollow frame is a rectangular parallelepiped hollow frame.
对应于上述骨架装置，本发明所述的具有该骨架装置的光纤陀螺惯性器件所采用的技术方案：包括光纤陀螺仪、电源模块、电路板和罩壳，所述光纤陀螺仪倒置固定于所述光纤陀螺仪容置腔内；所述电源模块和电路板均设置于所述电源组件容置腔，并固定于所述环式固定支撑件上；光纤陀螺仪的线路穿过所述散热接线孔后连接在所述电路板上；所述罩壳自上而下罩设在所述镂空框架外部，并与所述底座密封连接。Corresponding to the above-mentioned skeleton device, the technical solution adopted by the fiber optic gyroscope inertial device with the skeleton device according to the present invention: includes a fiber optic gyroscope, a power module, a circuit board and a cover, and the fiber optic gyroscope is fixed upside down on the The fiber optic gyroscope accommodating cavity; the power module and the circuit board are both arranged in the power component accommodating cavity and fixed on the ring-type fixed support; after the fiber optic gyroscope line passes through the heat dissipation wiring hole It is connected to the circuit board; the cover is arranged on the outside of the hollow frame from top to bottom, and is hermetically connected with the base.
其中所述光纤陀螺仪的外径与所述光纤陀螺仪容置腔的内径一致。The outer diameter of the fiber optic gyroscope is consistent with the inner diameter of the accommodating cavity of the fiber optic gyroscope.
有益效果：该骨架装置设置有环式固定支撑件和中空且上端开口的镂空框架，通过环式固定支撑件将镂空框架的中空内腔分隔成光纤陀螺仪容置腔和电源组件容置腔，为光纤陀螺仪和电源组件提供合理的装配空间，避免空间布局的浪费。并在镂空框架的各个侧壁镂空开设散热孔，提供了足够的散热空间，光纤陀螺仪和电源组件工作散发的热量可以在侧壁和顶部的开孔处自由流动，避免因局部热量过高对测量精度产生影响，从而使得装配有该骨架装置的光纤陀螺惯性器件具有较高的可靠性和环境适应性。Beneficial effects: The frame device is provided with a ring-type fixed support and a hollow frame with a hollow and open upper end, and the hollow inner cavity of the hollow frame is divided into an optical fiber gyroscope accommodating cavity and a power supply component accommodating cavity by the ring-type fixed support. Fiber optic gyroscopes and power supply components provide reasonable assembly space to avoid waste of space layout. In addition, heat dissipation holes are hollowed out on each side wall of the hollow frame to provide enough heat dissipation space. The heat emitted by the fiber optic gyroscope and power supply assembly can flow freely at the openings on the side walls and the top to avoid excessive local heat. The measurement accuracy has an impact, so that the fiber optic gyroscope inertial device equipped with the skeleton device has higher reliability and environmental adaptability.
图1是本发明中骨架本体结构示意图；Figure 1 is a schematic diagram of the skeleton body structure of the present invention;
图2是本发明中骨架本体结构俯视示意图；Figure 2 is a schematic top view of the skeleton body structure of the present invention;
图3是本发明中环式固定支撑件的结构示意图；Figure 3 is a schematic view of the structure of the ring-type fixed support of the present invention;
图4是本发明的光纤陀螺惯性器件内部结构示意图；4 is a schematic diagram of the internal structure of the fiber optic gyroscope inertial device of the present invention;
图5是本发明中光纤陀螺仪结构示意图；5 is a schematic diagram of the structure of the fiber optic gyroscope in the present invention;
图6是本发明的光纤陀螺惯性器件整体结构示意图；6 is a schematic diagram of the overall structure of the fiber optic gyroscope inertial device of the present invention;
图7是本发明的光纤陀螺惯性器件内部结构***图。Fig. 7 is an exploded view of the internal structure of the fiber optic gyroscope inertial device of the present invention.
下面，结合附图对本发明做进一步详细说明。Hereinafter, the present invention will be further described in detail with reference to the accompanying drawings.
如图1-7所示，本实施例公开一种光纤陀螺惯性器件，该光纤陀螺惯性器件具有骨架装置、光纤陀螺仪10、电源模块11、电路板12和罩壳13。As shown in FIGS. 1-7, this embodiment discloses an optical fiber gyroscope inertial device, which has a skeleton device, an optical fiber gyroscope 10, a power module 11, a circuit board 12, and a cover 13.
其中，骨架装置包括骨架本体1和环式固定支撑件2。Among them, the skeleton device includes a skeleton body 1 and a ring-type fixed support 2.
请参阅图1和图2，该骨架本体1具有底座3和镂空框架4，该镂空框架4自底座3的上表面向上延伸出。Please refer to FIGS. 1 and 2, the skeleton body 1 has a base 3 and a hollow frame 4, and the hollow frame 4 extends upward from the upper surface of the base 3.
镂空框架4呈中空且顶端开口的长方体形结构，其四个侧壁的内表面中间位置均设置有凹台43，相邻的两个侧壁的内表面连接处设置有装配平台44。凹台43和装配平台44位于同一水平面，该水平面限定了支撑件装配平面在镂空框架4内部的位置。镂空框架4的侧壁上开设有上部散热孔41和下部散热孔42。环式固定支撑件2安装于该支撑件装配平面内，将镂空框架4的中空内腔分隔成位于下部的 光纤陀螺仪容置腔以及位于上部的电源组件容置腔。上部散热孔41连通电源组件容置腔，下部散热孔42连通光纤陀螺仪容置腔。The hollow frame 4 has a hollow rectangular parallelepiped structure with an open top. A recess 43 is provided in the middle of the inner surface of the four side walls, and an assembly platform 44 is provided at the junction of the inner surfaces of two adjacent side walls. The recess 43 and the assembly platform 44 are located on the same horizontal plane, and the horizontal plane defines the position of the support assembly plane inside the hollow frame 4. The side wall of the hollow frame 4 is provided with an upper heat dissipation hole 41 and a lower heat dissipation hole 42. The ring-type fixed support 2 is installed in the assembly plane of the support, and separates the hollow cavity of the hollow frame 4 into a fiber optic gyroscope accommodating cavity at the lower part and a power supply component accommodating cavity at the upper part. The upper heat dissipation hole 41 communicates with the power supply assembly accommodating cavity, and the lower heat dissipation hole 42 communicates with the fiber optic gyroscope accommodating cavity.
请一并参阅图3，环式固定支撑件2具有支撑件主体21、散热接线孔22、定位侧翼23和多个螺栓孔24。支撑件主体21的四个角分别设置在四个装配平台44上，四个定位侧翼23分别卡设在四个凹台43内，从而将环式固定支撑件2固定。散热接线孔22开设于支撑件主体21的中间位置，一方面用于布设线路，另一方面为下部光纤陀螺仪容置腔内的热量提供向上流动的通路。螺栓孔24分散布置在环式固定支撑件2的上表面，分别用于固定电源模块11和电路板12，且固定电源模块11和固定电路板12的螺栓孔24错位排布，两者之间具有足够的距离，互不形成干涉。Please also refer to FIG. 3, the ring-type fixed support 2 has a support main body 21, a heat dissipation wiring hole 22, a positioning side wing 23 and a plurality of bolt holes 24. The four corners of the support body 21 are respectively arranged on the four assembly platforms 44, and the four positioning side wings 23 are respectively clamped in the four recessed platforms 43, so that the ring-type fixed support 2 is fixed. The heat dissipation wiring hole 22 is opened in the middle position of the support body 21, on the one hand, it is used for wiring wiring, and on the other hand, it provides an upward flow path for the heat in the accommodating cavity of the lower fiber optic gyroscope. The bolt holes 24 are scattered on the upper surface of the ring-type fixing support 2, and are used to fix the power module 11 and the circuit board 12, and the bolt holes 24 for fixing the power module 11 and the circuit board 12 are arranged in a staggered manner. There is enough distance to not interfere with each other.
如图5所示，光纤陀螺仪10大致呈圆柱体结构，其侧壁上设置有与连接螺柱45配合的螺孔101，连接螺柱45设置在装配平台44下方的侧壁内表面连接处，通过螺丝将两者连接即可实现光纤陀螺仪10的固定。As shown in FIG. 5, the fiber optic gyroscope 10 has a roughly cylindrical structure, and its side wall is provided with a screw hole 101 that is matched with a connecting stud 45, and the connecting stud 45 is arranged at the connection of the inner surface of the side wall below the assembly platform 44 , The fiber optic gyroscope 10 can be fixed by connecting the two with screws.
结合如图4和图7，光纤陀螺仪10内嵌倒置安装在光纤陀螺仪容置腔内，镂空框架4的侧壁内表面呈圆弧形的部分抵靠在光纤陀螺仪10的外周，该部分的直径与光纤陀螺仪10的外径一致，从而避免加工制作或装配时两者之间缝隙过大造成空间和尺寸的浪费。In combination with Figures 4 and 7, the fiber optic gyroscope 10 is installed upside down in the fiber optic gyroscope housing cavity, and the arc-shaped part of the inner surface of the side wall of the hollow frame 4 abuts against the outer circumference of the fiber optic gyroscope 10. The diameter of is consistent with the outer diameter of the fiber optic gyroscope 10, so as to avoid excessive space and size waste due to excessive gaps between the two during manufacturing or assembly.
由电源模块11和电路板12组成的电源组件设置于电源组件容置腔内，并分别通过螺丝15连接固定在环式固定支撑件2的不同螺栓孔24上。光纤陀螺仪10的线路穿过散热接线孔22后连接在电路板 12上，并通过电源模块11提供电能。电路板12通过环式固定支撑件2与光纤陀螺仪10固定，实现共振，可减少影响光纤陀螺仪10测量精度的额外因素。The power supply assembly composed of the power supply module 11 and the circuit board 12 is arranged in the power supply assembly accommodating cavity, and is connected and fixed to different bolt holes 24 of the ring-type fixing support 2 by screws 15 respectively. The line of the fiber optic gyroscope 10 passes through the heat dissipation wiring hole 22 and then is connected to the circuit board 12, and the power module 11 provides power. The circuit board 12 is fixed to the fiber optic gyroscope 10 through the ring-type fixed support 2 to achieve resonance, which can reduce additional factors that affect the measurement accuracy of the fiber optic gyroscope 10.
最后请参阅图6所示，罩壳13自上而下罩设在镂空框架4外部，通过密封圈与底座3进行密封，通过螺丝连接两者的固定耳以完成装配固定。概罩壳13用于防潮以及提高光纤陀螺惯性器件的抗冲击性，其厚度较薄不会对散热产生影响。Finally, please refer to FIG. 6, the cover 13 is arranged on the outside of the hollow frame 4 from top to bottom, and is sealed with the base 3 by a sealing ring, and the fixing ears of the two are connected by screws to complete the assembly and fixing. The general cover 13 is used to prevent moisture and improve the impact resistance of the fiber optic gyroscope inertial device, and its thin thickness will not affect heat dissipation.
Claims (10)
- 一种骨架装置，其特征在于，包括骨架本体(1)和环式固定支撑件(2)；所述骨架本体(1)具有底座(3)、自底座(3)上表面向上延伸出的镂空框架(4)；所述镂空框架(4)呈中空且顶端开口的结构，镂空框架(4)内具有支撑件装配平面；所述环式固定支撑件(2)安装于该支撑件装配平面上，并将镂空框架(4)的中空内腔分隔出上下两个腔室，所述两个腔室分别为位于下部的光纤陀螺仪容置腔以及位于上部的电源组件容置腔；所述镂空框架(4)的各个侧壁均具有上部散热孔(41)和下部散热孔(42)，所述上部散热孔(41)贯通至所述电源组件容置腔，所述下部散热孔(42)贯通至所述光纤陀螺仪容置腔。A skeleton device, characterized in that it comprises a skeleton body (1) and a ring-type fixed support (2); the skeleton body (1) has a base (3) and a hollow extending upward from the upper surface of the base (3) Frame (4); the hollow frame (4) has a hollow structure with an open top, and the hollow frame (4) has a support assembly plane; the ring-type fixed support (2) is installed on the support assembly plane , And separate the hollow inner cavity of the hollow frame (4) into two upper and lower chambers, the two chambers are the fiber optic gyroscope accommodating cavity at the lower part and the power supply component accommodating cavity at the upper part; the hollow frame (4) Each side wall has an upper heat dissipation hole (41) and a lower heat dissipation hole (42). The upper heat dissipation hole (41) penetrates to the power supply assembly accommodating cavity, and the lower heat dissipation hole (42) penetrates To the accommodating cavity of the fiber optic gyroscope.
- 根据权利要求1所述的骨架装置，其特征在于，所述镂空框架(4)的各个侧壁的内表面均设置有凹台(43)，相邻的两个所述侧壁的内表面连接处均具有装配平台(44)，所述凹台(43)和所述装配平台(44)位于同一水平面，凹台(43)和装配平台(44)共同形成所述支撑件装配平面。The skeleton device according to claim 1, characterized in that the inner surface of each side wall of the hollow frame (4) is provided with a recess (43), and the inner surfaces of two adjacent side walls are connected An assembly platform (44) is provided at each location, and the recessed platform (43) and the assembling platform (44) are located on the same horizontal plane, and the recessed platform (43) and the assembling platform (44) jointly form the support assembly plane.
- 根据权利要求2所述的骨架装置，其特征在于，所述环式固定支撑件(2)具有支撑件主体(21)和散热接线孔(22)，所述支撑件主体(21)设置在所述装配平台(44)上，所述散热接线孔(22)贯穿的设置于支撑件主体(21)的中间位置。The skeleton device according to claim 2, characterized in that the ring-type fixed support (2) has a support main body (21) and a heat dissipation wiring hole (22), and the support main body (21) is arranged at the On the assembling platform (44), the heat dissipation wiring hole (22) is penetrated and arranged at the middle position of the support body (21).
- 根据权利要求3所述的骨架装置，其特征在于，所述环式固定支撑件(2)还具有与所述凹台(43)一一对应的定位侧翼(23)，所 述定位侧翼(23)自所述支撑件主体(21)向对应的凹台(43)延伸，并卡设在凹台(43)内。The skeleton device according to claim 3, characterized in that the ring-type fixed support (2) further has positioning flanks (23) corresponding to the concave platform (43) one-to-one, and the positioning flanks (23) ) Extends from the support body (21) to the corresponding recess (43), and is clamped in the recess (43).
- 根据权利要求3所述的骨架装置，其特征在于，所述环式固定支撑件(2)还具有多个用于安装固定电源组件的螺栓孔(24)，所述螺栓孔(24)分散布置于该环式固定支撑件(2)的表面。The skeleton device according to claim 3, characterized in that the ring-type fixed support (2) further has a plurality of bolt holes (24) for installing and fixing the power supply assembly, and the bolt holes (24) are distributedly arranged On the surface of the ring-type fixing support (2).
- 根据权利要求2所述的骨架装置，其特征在于，所述镂空框架(4)的相邻的两个侧壁的内表面连接处设置有用于固定光纤陀螺仪(10)的连接螺柱(45)，所述连接螺柱(45)位于所述装配平台(44)下方。The skeleton device according to claim 2, characterized in that the inner surface of the two adjacent side walls of the hollow frame (4) is connected with a connecting stud (45) for fixing the fiber optic gyroscope (10). ), the connecting stud (45) is located below the assembly platform (44).
- 根据权利要求1所述的骨架装置，其特征在于，所述镂空框架(4)位于所述支撑件装配平面下方的侧壁内表面具有呈圆弧形的部分，该部分限定了所述光纤陀螺仪容置腔的内径。The skeleton device according to claim 1, characterized in that the inner surface of the side wall of the hollow frame (4) located below the mounting plane of the support has an arc-shaped part which defines the fiber optic gyro The inner diameter of the chamber.
- 根据权利要求1-7任一项所述的骨架装置，其特征在于，所述镂空框架(4)为长方体形镂空框架。The skeleton device according to any one of claims 1-7, wherein the hollow frame (4) is a rectangular parallelepiped hollow frame.
- 一种具有权利要求1-8任一项所述骨架装置的光纤陀螺惯性器件，其特征在于，包括光纤陀螺仪(10)、电源模块(11)、电路板(12)和罩壳(13)，所述光纤陀螺仪(10)倒置固定于所述光纤陀螺仪容置腔内；所述电源模块(11)和电路板(12)均设置于所述电源组件容置腔内，并固定于所述环式固定支撑件(2)上；光纤陀螺仪(10)的线路穿过所述散热接线孔(22)后连接在所述电路板(12)上；所述罩壳(13)自上而下罩设在所述镂空框架(4)外部，并与所述底座(3)密封连接。An optical fiber gyroscope inertial device with the skeleton device of any one of claims 1-8, characterized in that it comprises an optical fiber gyroscope (10), a power module (11), a circuit board (12) and a cover (13) , The fiber optic gyroscope (10) is fixed in the accommodating cavity of the fiber optic gyroscope upside down; the power module (11) and the circuit board (12) are both arranged in the accommodating cavity of the power supply assembly and fixed in the The ring-type fixed support (2); the line of the fiber optic gyroscope (10) passes through the heat dissipation wiring hole (22) and then is connected to the circuit board (12); the cover (13) is from above The lower cover is arranged outside the hollow frame (4) and is connected to the base (3) in a sealed manner.
- 根据权利要求9所述的光纤陀螺惯性器件，其特征在于，所述光纤陀螺仪(10)的外径与所述光纤陀螺仪容置腔的内径一致。The fiber optic gyroscope inertial device according to claim 9, characterized in that the outer diameter of the fiber optic gyroscope (10) is consistent with the inner diameter of the fiber optic gyroscope containing cavity.
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| CN201910565512.5 | 2019-06-26 | ||
| CN201910565512.5A CN110260852B (en) | 2019-06-26 | 2019-06-26 | Framework device and fiber-optic gyroscope inertial device with same |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113375654A (en) * | 2021-04-29 | 2021-09-10 | 北京航天时代光电科技有限公司 | Light and small optical fiber gyroscope with good environmental adaptability |
| CN113514082A (en) * | 2021-07-14 | 2021-10-19 | 中国人民解放军国防科技大学 | Assembly fixture, assembly system and assembly method for micro-hemispherical resonant gyroscope structure |
| CN113945226A (en) * | 2021-08-31 | 2022-01-18 | 北京航天时代光电科技有限公司 | High-precision double-light-source redundant triaxial integrated fiber optic gyroscope measuring device structure |
| CN114018256A (en) * | 2021-11-03 | 2022-02-08 | 东南大学 | Optical fiber/MEMS dual-mode inertial-based navigation hardware system device |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260852B (en) * | 2019-06-26 | 2021-09-28 | 东南大学 | Framework device and fiber-optic gyroscope inertial device with same |
| CN110672084A (en) * | 2019-11-20 | 2020-01-10 | 衡阳市和仲通讯科技有限公司 | Active heat dissipation optical fiber gyroscope framework |
| CN111044028B (en) * | 2020-01-09 | 2023-05-09 | 陕西华燕航空仪表有限公司 | Triaxial fiber optic gyroscope |
| CN114696138A (en) * | 2022-04-11 | 2022-07-01 | 宁波公牛电器有限公司 | Socket |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08313271A (en) * | 1995-05-17 | 1996-11-29 | Japan Aviation Electron Ind Ltd | Fiber-optic coil |
| CN101922938A (en) * | 2010-07-14 | 2010-12-22 | 北京航空航天大学 | High-precision laser gyroscope inertia measurement system for POS |
| CN103063408A (en) * | 2012-12-21 | 2013-04-24 | 天津光拓科技有限公司 | Integrated optical fiber loop testing system |
| CN103114845A (en) * | 2013-01-17 | 2013-05-22 | 北京航空航天大学 | Fiber-optic gyroscope inertial measurement unit (IMU) framework for oil clinometer |
| CN105300372A (en) * | 2015-11-06 | 2016-02-03 | 北京航天时代光电科技有限公司 | Photoelectric separation fiber optic gyroscope |
| CN110260852A (en) * | 2019-06-26 | 2019-09-20 | 东南大学 | Frame device and optical fibre gyro inertia device with the frame device |
-
2019
- 2019-06-26 CN CN201910565512.5A patent/CN110260852B/en active Active
-
2020
- 2020-04-15 WO PCT/CN2020/084845 patent/WO2020259010A1/en active Application Filing
- 2020-04-15 LU LU101990A patent/LU101990B1/en active IP Right Grant
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08313271A (en) * | 1995-05-17 | 1996-11-29 | Japan Aviation Electron Ind Ltd | Fiber-optic coil |
| CN101922938A (en) * | 2010-07-14 | 2010-12-22 | 北京航空航天大学 | High-precision laser gyroscope inertia measurement system for POS |
| CN103063408A (en) * | 2012-12-21 | 2013-04-24 | 天津光拓科技有限公司 | Integrated optical fiber loop testing system |
| CN103114845A (en) * | 2013-01-17 | 2013-05-22 | 北京航空航天大学 | Fiber-optic gyroscope inertial measurement unit (IMU) framework for oil clinometer |
| CN105300372A (en) * | 2015-11-06 | 2016-02-03 | 北京航天时代光电科技有限公司 | Photoelectric separation fiber optic gyroscope |
| CN110260852A (en) * | 2019-06-26 | 2019-09-20 | 东南大学 | Frame device and optical fibre gyro inertia device with the frame device |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113375654A (en) * | 2021-04-29 | 2021-09-10 | 北京航天时代光电科技有限公司 | Light and small optical fiber gyroscope with good environmental adaptability |
| CN113514082A (en) * | 2021-07-14 | 2021-10-19 | 中国人民解放军国防科技大学 | Assembly fixture, assembly system and assembly method for micro-hemispherical resonant gyroscope structure |
| CN113514082B (en) * | 2021-07-14 | 2022-07-12 | 中国人民解放军国防科技大学 | Assembly fixture, assembly system and assembly method for micro-hemispherical resonant gyroscope structure |
| CN113945226A (en) * | 2021-08-31 | 2022-01-18 | 北京航天时代光电科技有限公司 | High-precision double-light-source redundant triaxial integrated fiber optic gyroscope measuring device structure |
| CN113945226B (en) * | 2021-08-31 | 2024-05-31 | 北京航天时代光电科技有限公司 | High-precision double-light-source redundant triaxial integrated fiber-optic gyroscope measuring device |
| CN114018256A (en) * | 2021-11-03 | 2022-02-08 | 东南大学 | Optical fiber/MEMS dual-mode inertial-based navigation hardware system device |
| CN114018256B (en) * | 2021-11-03 | 2024-01-02 | 东南大学 | Optical fiber/MEMS (micro-electromechanical systems) dual-mode inertial-based navigation hardware system device |
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